Technical Report Archive & Image Library (TRAIL) - 32,772 Matching Results

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Longitudinal Stability Investigation for a Mach Number Range of 0.8 to 1.7 of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail

Description: Report presenting an investigation of an airplane configuration model with a 45 degree swept wing of aspect ratio 4.0 and a taper ratio 0.3 with a low swept horizontal tail to determine its longitudinal stability. Longitudinal aerodynamic coefficients and stability derivatives are presented as functions of Mach number over the test range. The results are compared to wind tunnel and rocket model data and generally show good agreement.
Date: February 8, 1956
Creator: McFall, John C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Free-Flight Study of the Drag and Stability of a Series of Short-Span Missiles at Mach Numbers From 0.9 to 1.3

Description: Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.
Date: February 8, 1956
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A simulation study of a wingless missile

Description: Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.
Date: February 8, 1956
Creator: Lessing, Henry C. & Reese, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Transonic Speeds of a Jet Control on a 35 Degree Swept Wing: Transonic-Bump Method

Description: Report presenting an investigation in the high-speed tunnel using the transonic-bump method to determine the characteristics of a jet control consisting of numerous holes located at the 65-percent chord line of a 35 degree swept semispan wing with an NACA 65A006 airfoil section. Testing occurred over a range of Mach numbers, angles of attack, and ejection-pressure ratios. Results regarding rolling-moment coefficients and aerodynamic characteristics in pitch are provided.
Date: February 8, 1956
Creator: Vogler, Raymond D. & Turner, Thomas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102B Airplane at Mach Numbers of 1.41, 1.61, and 2.01: Coord No. AF-231

Description: Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Date: February 7, 1956
Creator: Driver, Cornelius & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift, drag, and static longitudinal stability characteristics of configurations consisting of three triangular wing panels and a body of equal length at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for three highly swept three-wing tailless configurations determined from tests at a range of Mach numbers and angles of attack.
Date: February 7, 1956
Creator: Savin, Raymond C. & Wong, Thomas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Modification of a 1706-KER Loop for Boiling

Description: It is the purpose of this report to: 1. Present the results of a study to estimate the range of attainable boiling conditions in the 1706 KER loop design on the bases given in reference (12). 2. Present an outline of the significant modifications and equipment changes necessary to obtain the process conditions desired.
Date: February 7, 1956
Creator: Tippets, F. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Results of the D-12 Boil Up Test and Recommendations to Improve the Performance of Bayonet Tube Bundles

Description: The purpose of this report is to describe the tests performed on the D-12 waste evaporator, to present and evaluate the data obtained during the test, and to make recommendations for the implementation and operation of present and future installations of bayonet tube bundles.
Date: February 7, 1956
Creator: Cook, M. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of a missile designed to fly at low speed with its longitudinal axis aligned with the flight path

Description: An experimental investigation to explore the practicability of a low-speed missile designed to fly with its longitudinal axis pointing along the flight path. The wing and tail surfaces were arranged in a cruciform pattern and the incidence was selected to trim the missile at the desired normal-force coefficient with the body at 0 degrees angle of attack. Results regarding the description of a self-balancing missile and experimental results are provided.
Date: February 7, 1956
Creator: Hopkins, Edward J. & Sorensen, Norman E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Probability and Extent of a Fission Product Release From a Power Reactor

Description: Report discussing both the probability of having a reactor accident that would release fission products, as well as the probable extent of the release of the products. This information, along with the contents of the fission products themselves, are based on statistical analysis and educated guesses.
Date: February 4, 1956
Creator: Fleck, Joseph A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of area-suction-type boundary-layer control on the landing-approach characteristics of a 35 degree swept-wing fighter

Description: Report presenting results of evaluation flights of F-86 series aircraft equipped with two types of boundary-layer control, which differed significantly in regards to the type of lift increment produced. The report presents the comments of 16 Air Force, Navy, contractor, and NACA pilots as to the reasons for their choice of minimum, comfortable approach speed on the several configurations tested.
Date: February 3, 1956
Creator: Cooper, George E. & Innis, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with area suction boundary-layer control on the flaps

Description: Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics o… more
Date: February 3, 1956
Creator: Anderson, Seth B. & Quigley, Hervey C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Limited Hydrodynamic Investigation of a 1/15-Size Model of a Modified Nose-Inlet Multijet Water-Based Aircraft

Description: Memorandum presenting an investigation conducted to determine the effect on the low-speed resistance and spray characteristics and static transverse stability of a modification which extended the bow of a scale model of a nose-inlet transonic seaplane configuration. The investigation was made with and without tip floats. The change was found to result in a 50-percent reduction in the hump resistance, increased engine-inlet clearance, reduced low-speed spray and hull-side flow, and acceptable sp… more
Date: February 3, 1956
Creator: McKann, Robert E. & Coffee, Claude W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-speed longitudinal stability and lateral-control characteristics of a model of a 40 degree swept-wing fighter-type airplane at a Reynolds number of 9 x 10(exp 6)

Description: Report presenting an investigation on a model of a 40 degree swept-wing fighter airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight testing. The effects of high-lift and stall control devices, horizontal-tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated.
Date: February 3, 1956
Creator: Bollech, Thomas V. & Kelly, H. Neale
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at High Subsonic Speeds of Some Effects of Fuselage Cross-Section Shape and Wing Height on the Static Longitudinal and Lateral Stability Characteristics of a Model Having a 45 Degree Swept Wing

Description: Report presenting an investigation in the high-speed tunnel at Mach numbers from 0.80 to 0.92 to determine the effects of fuselage shape on the aerodynamic characteristics of a model with low and high wing arrangements. Results regarding longitudinal stability characteristics and lateral stability characteristics of the different component combinations are provided.
Date: February 3, 1956
Creator: King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Acoustics of a Nonhomogeneous Moving Medium

Description: Report discussing theoretical basis of the acoustics of a moving nonhomogeneous medium. Experiments that illustrate or confirm some of the theoretical explanation or derivation of these acoustics are also included.
Date: February 1956
Creator: Blokhintsev, D. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures

Description: Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.
Date: February 1, 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Afterburner performance with combustion-chamber lengths from 10 to 62 inches at several afterburner-inlet temperatures

Description: Report presenting an investigation to determine the effect of variation of afterburner combustion-chamber length and inlet temperature on a low-pressure-loss sea-level afterburner.
Date: February 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bodies of revolution having minimum drag at high supersonic airspeeds

Description: Report presenting calculations of approximate shapes of nonlifting bodies having minimum pressure foredrag at higher supersonic airspeeds. The investigation is carried out for various combinations of the conditions of given body length, base diameter, surface area, and volume.
Date: February 1956
Creator: Eggers, A. J., Jr.; Resnikoff, Meyer M. & Dennis, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of landing-impact velocities of first and second wheel to contact from statistical measurements of transport airplane landings

Description: Report presenting a statistical analysis of vertical velocities at second wheel to touch made from photographs of 353 landings of transport airplanes at Washington National Airport. Results regarding gusts, rolling direction, and number of engines are provided.
Date: February 1956
Creator: Harrin, Eziaslav N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cross flows in laminar incompressible boundary layers

Description: Report presenting an analysis derived for the three-dimensional boundary-layer flow over a flat surface with a leading edge under main-flow streamlines that are translates and representable by polynomial expressions. The boundary layers are laminar and incompressible and the profiles of their velocity components have similarity with respect to rectangular coordinates.
Date: February 1956
Creator: Hansen, Arthur G. & Herzig, Howard Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of pneumatic de-icers and ice formations on aerodynamic characteristics of a airfoil

Description: Report presenting measurements of lift, drag, and pitching moment of an NACA 0011 airfoil in icing using two types of pneumatic de-icers, one with spanwise inflatable tubes and the other with chordwise tubes. Results regarding the airfoil characteristics with the de-icer operating and effect of primary ice formation on drag, lift, and pitch with the de-icer inoperative are provided.
Date: February 1956
Creator: Bowden, Dean T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Transverse Body Force on Channel Flow With Small Heat Addition

Description: Note presenting an analysis of the steady, compressible, inviscid channel flow to which heat is added at a cross-sectional plane and which is also subject to a transverse body force. The prime parameters governing the flow are a dimensionless heat parameter and the Mach and Froude numbers. Solutions were obtained for uniform or nonuniform heat addition at a cross-sectional plane under the simplifying assumption of either small Mach number or large Froude number.
Date: February 1956
Creator: Ostrach, Simon & Moore, Franklin K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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